EP4083433A1 - Ventilateur et aubes de ventilateur - Google Patents

Ventilateur et aubes de ventilateur Download PDF

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Publication number
EP4083433A1
EP4083433A1 EP22178084.4A EP22178084A EP4083433A1 EP 4083433 A1 EP4083433 A1 EP 4083433A1 EP 22178084 A EP22178084 A EP 22178084A EP 4083433 A1 EP4083433 A1 EP 4083433A1
Authority
EP
European Patent Office
Prior art keywords
leading edge
wave
fan blade
fan
corrugated
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
EP22178084.4A
Other languages
German (de)
English (en)
Inventor
Marc Schneider
Andreas LUCIUS
Marius Lehmann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ebm Papst Mulfingen GmbH and Co KG
Original Assignee
Ebm Papst Mulfingen GmbH and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Ebm Papst Mulfingen GmbH and Co KG filed Critical Ebm Papst Mulfingen GmbH and Co KG
Publication of EP4083433A1 publication Critical patent/EP4083433A1/fr
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/281—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for fans or blowers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/16—Centrifugal pumps for displacing without appreciable compression
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/002—Axial flow fans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • F04D29/386—Skewed blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/388—Blades characterised by construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/663—Sound attenuation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/06—Helico-centrifugal pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • F05D2250/611—Structure; Surface texture corrugated undulated
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction

Definitions

  • the present invention relates to a fan and a fan blade, in particular for an axial fan or diagonal fan.
  • the turbulent inflow to the fan leads to a significant increase in noise emissions, which means annoying noise development.
  • the degree of turbulence Tu and the so-called turbulent linear measure ⁇ can be determined by measurement.
  • the degree of turbulence is the ratio of the magnitude of the fluctuation in velocity to the mean.
  • the turbulent length measure is the mean dimension of the turbulent structures. It corresponds the path length over which velocity fluctuations are correlated.
  • the heat exchanger is essentially made up of tubes with fins.
  • the pamphlet DE 19948075 A uses an axial fan with blades that have a double-sickled, leading blade edge with a protruding outer corner to reduce running noise.
  • the US 3416725A shows a wing shape with a double-sickled leading edge and a slightly single-sickled trailing edge.
  • the DE 10326637 B3 describes a further solution, namely a fan with alternating direction of rotation, which has S-shaped sickled blades with the leading edge receding sharply towards the outside.
  • the WO 1998005868 A1 discloses a numerical method for aeroacoustic optimization of an axial fan or its blade geometry and the US2649921 provides a fan with very short and wide blades and triple curved leading and trailing edges.
  • the US5533865A a rotor for a wind turbine, the blades of which have sawtooth-shaped trailing edges. Serrated or wavy trailing edges are used to reduce trailing edge noise (eg GB2497739 or EP 1801422 A2 ).
  • the DE 102009044824 A1 uses porosities in the form of holes in the area of the trailing edge to reduce noise generation at the trailing edge.
  • Corrugated or jagged leading edges are also known as a means of reducing noise in turbulent flow.
  • the US6431498B1 describes a wavy leading edge that is created by various cuts in the spanwise direction. The front area is lengthened in the direction of the chord up to the maximum thickness.
  • the US 9249 666 B2 describes an alternative design of the wave on the leading edge, in which the profile is not lengthened in the chord direction, but leaves the reference profile on the pressure or suction side.
  • a special leading edge wave in the form of a double sine is used in EP 3121 376 B1 described.
  • the WO2013/180296 uses serrated leading edges with a triangular shape.
  • the pamphlet DE 102017212231 A1 describes a combination of a corrugated leading edge with a corrugated trailing edge. The waves on the leading edge have larger wavelengths compared to the trailing edge.
  • the wave trough is an important place of noise generation with wavy or jagged leading edges.
  • Other writings deal with modifications of the shovel in the area of the valley.
  • the JP6409666B2 uses additional vanes on the blade in the valley area.
  • JP5978886B2 describes a relief of the jagged leading edge in the valley.
  • the invention deals with the problem of providing a ventilator or ventilator blade which operates with little noise, particularly in the case of turbulent inflow, and which at the same time has good aerodynamic properties.
  • the invention solves this problem with a fan according to the independent claims.
  • the dependent claims contain advantageous developments.
  • a typical axial or diagonal fan with mostly several fan blades arranged in a star shape on a central hub for aerodynamic suction and/or pressure of the air surrounding the fan or a gas to be conveyed by the fan.
  • the fan blades can be connected to one another by a circumferential ring on the radially outermost profile surface.
  • each fan blade has a front leading edge, which leads in the intended direction of rotation during operation, and a rear trailing edge, which lags in the intended direction of rotation during operation of the fan.
  • there is a suction side and a pressure side where the suction side is typically on the convex side and the pressure side is typically on the concave side of the fan blade.
  • the inflow and outflow edges are usually only optimally shaped for one direction of rotation.
  • the fan blade blade has a suction side, which sucks in the incoming air during operation, and a pressure side opposite the suction side, on which the pressure for ejecting the air builds up.
  • the fan according to the invention is distinguished from a comparable conventional fan by a noise-reduced operation with turbulent inflow.
  • a ventilator according to the invention uses at least one ventilator blade according to the invention, with this achieving reduced noise during operation compared to comparable conventional ventilators due to a special shape.
  • the mechanism of increased noise generation is based on the fact that the turbulent inflow is associated with a change in the inflow of the fan over time.
  • the turbulence leads to fluctuations in the forces occurring on the wing over time, as a result of which a corresponding vibration-like sound emission is triggered. Of particular importance is the intensity of such fluctuations.
  • the present invention aims at a specific design of the leading edge shaft that is acoustically and aerodynamically advantageous. It has been shown according to the invention that the formation of a very specific waveform is particularly advantageous.
  • leading edge has, at least in sections, a specific three-dimensional wave-shaped form or is three-dimensionally wave-shaped.
  • the special design of the shaft differs significantly from the prior art. It is also advantageous if the corrugated leading edge is also designed with a porosity.
  • a fan blade is provided with a leading edge and a trailing edge, with the fan blade having a corrugated leading edge at least in a partial area with a periodically repeating waveform of period length ⁇ , which deviates from a sinusoidal or almost sinusoidal waveform, in particular deviating from a sinusoidal or almost sinusoidal Waveform with the same period length ⁇ is.
  • the period is the smallest local distance after which the phenomenon is repeated.
  • the corrugated leading edge has two or more periodically repeating corrugations for this purpose.
  • the effect according to the invention occurs when the desired waveform is formed over a number of periods.
  • alternating troughs and crests at the leading edge d. H. be formed along the leading edge, which are provided in a certain periodicity.
  • the optimal range of wavelength and amplitude was determined from experimental tests, which brings both aerodynamic and acoustic improvements at the same time.
  • the so-called peak-to-valley value H of the wave is the distance from the highest point to the lowest point.
  • waves with large heights large peak-to-valley H
  • smaller wavelengths small ⁇ /H
  • Small peak-to-valley values H and larger wavelengths are advantageous for reducing the recording power.
  • preferred peak/valley values H in the range of 0.01 ⁇ H/D ⁇ 0.1 are advantageous.
  • the peak-valley value H of the wave troughs is defined from the front edge in this area of the wavy leading edge to the respective wave trough (viewed in the direction of flow) and values for the ratio between the period length ⁇ and in the range 0.2 ⁇ ⁇ /H ⁇ 2 with the peak-to-valley value H, where the values can vary along the leading edge.
  • a solution has proven to be particularly effective in which a waveform deviating from a sinusoidal shape is provided with deep-cut wave troughs per period, ie sufficiently large wave troughs.
  • the amplitude or the peak-to-valley value should have a certain value compared to the chord length of the fan blade. Slightly pronounced or only sinusoidal wave troughs have not proven to be sufficiently effective. Rather, the peak-valley value of the wave troughs in the region of the wavy leading edge should preferably be approximately 10%-30% of the chord length SL, more preferably 10% to 20% of the chord length SL. Compared to an imaginary sine wave with the same number of periods, the peak-valley value should therefore be larger, which leads to steeper edges compared to the direction of flow in the wave trough.
  • the repetitive waveform per period forms at least one trough with two "steep" wave flanks running towards one another and in each case at an angle to the direction of flow. It is particularly advantageous here if the (lateral) wave flanks running obliquely to the wave trough in this area of the leading edge (especially in a section near the middle of the flank) are at a tangential angle ⁇ of between 15° and 35°, preferably a tangential angle ⁇ of 25 ° up to 30°.
  • the repetitive waveform (i.e., the waveform that is periodically arranged) forms two adjacent troughs with an intermediate crest extending upstream toward the upstream leading edge.
  • the two lateral flanks that delimit this waveform are correspondingly slanted, as previously explained.
  • the following procedure can be followed for the construction of the shaft, namely that the waveform in the region of the corrugated leading edge runs at least partially or completely through several, in particular six, common points of intersection (support points) with an imaginary sine wave, in its shape deviates from a sine wave.
  • the peak-valley value h2 of such a wave crest is approximately 10% to 80% of the peak-valley value H of the immediately adjacent wave crest or crests.
  • the wavy leading edge is approximately in the middle of a period d. H. to adapt locally to the flow at half wavelength.
  • an offset of the leading edge perpendicular to the center line between the pressure side and the suction side of the wing is introduced. This offset improves the flow towards the leading edge and helps to avoid flow separation in this area.
  • This offset is preferably carried out in the direction of the pressure side.
  • the wing profile also has a specific, in particular wavy, structure in certain sections in addition to the wavy leading edge.
  • the wing profile (viewed in a profile section in the area of a wave crest) can have a bulge protruding from the suction side (SS) and a dent extending into it on the pressure side (DS), the surface profile of which is defined in such a way that the surface curvature changes twice when viewed in the direction of flow . If the surface profile on the upper side (suction side) corresponds approximately to the opposite surface profile on the underside (pressure side), the wing profile has an approximately constant thickness, but bulges slightly on the suction side.
  • a further improvement can lie in the fact that the wing profile curves further towards the pressure side at the end in the area of the leading edge (viewed in a profile section) compared to the area or an adjacent area that is less curved towards the pressure side.
  • a specific additional wavy structure of the vane is achieved, preferably with a spacing of one period, more preferably from one period center to one period center.
  • the fan blade is designed in the area of the leading edge with a large number of channels running through the fan blade from the pressure side to the suction side (area with porosity).
  • porosities in the area of the blade edges interacting with the turbulence, a further reduction in the sound radiation can be achieved, and these can be formed by holes or slots. These are continuous openings that allow pressure equalization between the suction and pressure sides of the fan blade.
  • the hole diameter or the width of the slots assume values in a range of up to approximately 2 mm.
  • the porous area preferably comprises only a partial area of the leading edge, the partial area being less than about 20% of the blade length.
  • a combination of a plurality of geometric design elements according to the invention is particularly advantageous, in which case the special features specific to the invention must be taken into account in each case.
  • the special features specific to the invention must be taken into account in each case.
  • a combination of porosity and a three-dimensional corrugation in the area of the leading edge is possible.
  • the present invention relates in particular to an axial or diagonal fan which has one or more fan blades as described above.
  • the figure 1 shows a fan blade 1 with partially corrugated leading edge.
  • the fan blade 1 has a leading edge 2, 4 and a trailing edge 3 as well as an at least partially corrugated area on the leading edge, which is referred to as a corrugated leading edge 4, this area of the leading edge 4 forming a specific wave shape.
  • 2* denotes the leading edge of a reference wing without a wavy leading edge.
  • the reference wing represents a non-optimized wing without the features of the present invention.
  • two circumferential profile section lines A and B are drawn.
  • the position of the profile section A is chosen so that the chord length of the fan blade 1 with the corrugated leading edge 4 is approximately the chord length of a reference blade with a non-corrugated leading edge 2*.
  • the position of the profile section B is chosen so that it runs through a wave crest of the fan blade 1 with the corrugated leading edge 4 .
  • the figure 2 is a detailed view of the profile section B in the region of the corrugated leading edge 4 of the fan blade 1 to explain an S-shaped wave impact.
  • the profile with the wavy leading edge 4 leaves the reference profile with the non-wavy leading edge 2* close to the leading edge in the direction of the pressure side DS and further downstream in the direction of the suction side SS.
  • a measure is described below as to how the waveform at the leading edge can be derived or optimized based on a sine wave.
  • the waveform is defined by a number of support points S of the sine curve and the course of the curve results from spline interpolation.
  • the peak-to-valley H of wave 6 is the distance from the highest point to the lowest point.
  • the deviation from the sine wave is defined by a length h1 and the choice of the support points S.
  • This waveform 6 causes a trough 7 of the waveform 6 that is cut deeper in relation to the peak-valley value H.
  • the two flanks falling to the trough 7 are closer together and their position is steeper in relation to the direction of the inflow velocity v compared to the sine wave.
  • the effective inflow velocity i.e. the component of the inflow velocity v perpendicular to the leading edge, with which the disturbance hits the leading edge of the fan blade, is reduced if the edge is steeper. This leads to a more effective reduction of the emitted sound.
  • figure 4 shows another alternative variation of the location of the support points.
  • the base in the middle of the wave it is positioned upstream against the inflow direction, so that an additional wave crest 8 results in the middle of the wave.
  • the deviation from the sine wave is defined by a length h2 and the choice of the support points S.
  • figure 5 shows a configured fan blade 1 with a partially corrugated leading edge 4 with additional wave crests 8.
  • the drawn circumferential profile section with the profile section line C is selected so that it runs through an additional wave crest 8 of the fan blade 1 with the corrugated leading edge 4.
  • the figure 6 is a detailed view of the profile section C in the area of the corrugated leading edge of the fan blade 1 to explain a local adjustment of the blade profile in the area of the leading edge to the inflow.
  • the profile section is in the area of the original leading edge 4 essentially perpendicular to the center line between the pressure side and the suction side of the blade shifted by the length h3 in the direction of the pressure side DS.
  • the profile section adapted in this way with a modified leading edge 9 prevents flow separation and the associated noise emissions.
  • the advantageous adaptation of the profile section described is preferably in the middle of the wave, ie it can be both in the area of the additional wave crest 8 and in the area of the valley 7 .
  • the 7 shows an exemplary axial fan having five fan blades 1.
  • the 8 shows an exemplary diagonal fan with a rotating ring 10 having five fan blades 1.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP22178084.4A 2020-03-10 2021-03-04 Ventilateur et aubes de ventilateur Ceased EP4083433A1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102020106534 2020-03-10
EP21710900.8A EP4034770A1 (fr) 2020-03-10 2021-03-04 Ventilateur et pales de ventilateur
PCT/EP2021/055473 WO2021180559A1 (fr) 2020-03-10 2021-03-04 Ventilateur et pales de ventilateur

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
EP21710900.8A Division EP4034770A1 (fr) 2020-03-10 2021-03-04 Ventilateur et pales de ventilateur
EP21710900.8A Division-Into EP4034770A1 (fr) 2020-03-10 2021-03-04 Ventilateur et pales de ventilateur

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KR (4) KR20220146705A (fr)
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KR102710172B1 (ko) * 2020-03-13 2024-09-25 엘지전자 주식회사 팬모듈 및 이를 구비하는 휴대형 공기정화기
CN114608045B (zh) * 2022-03-24 2023-04-07 西安交通大学 一种集成灶的进气风道结构及集成灶
DE202022106417U1 (de) 2022-11-15 2022-12-13 Oliver Schmitz Axiallüfter
DE102022130248B3 (de) * 2022-11-15 2024-02-15 Oliver Schmitz Axiallüfter

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US2649921A (en) 1949-05-10 1953-08-25 Guy S Faber Propeller for fluid
US3416725A (en) 1967-10-12 1968-12-17 Acme Engineering And Mfg Corp Dihedral bladed ventilating fan
JPS649666B2 (fr) 1981-11-09 1989-02-20 Denshi Keisanki Kippon Gijutsu Kenkyu Kumiai
US5533865A (en) 1993-11-04 1996-07-09 Stork Product Engineering B.V. Wind turbine
WO1998005868A1 (fr) 1996-08-01 1998-02-12 Deutsches Zentrum für Luft- und Raumfahrt e.V. Procede d'optimisation aeroacoustique d'un ventilateur axial
DE19948075A1 (de) 1998-10-08 2000-05-25 Gate Spa Axial-Lüfterrad, insbesondere für Motorfahrzeuge
US6431498B1 (en) 2000-06-30 2002-08-13 Philip Watts Scalloped wing leading edge
DE10326637B3 (de) 2003-06-11 2005-01-13 Bayerische Motoren Werke Ag Kühlvorrichtung für ein Kraftfahrzeug
EP1801422A2 (fr) 2005-12-22 2007-06-27 Ziehl-Abegg AG Ventilateur et aube de ventilateur
DE102009044824A1 (de) 2008-12-11 2010-06-17 Zhongshan Broad-Ocean Motor Co., Ltd. Lüfterflügel
GB2497739A (en) 2011-12-19 2013-06-26 Rolls Royce Plc Rotor blade with serrated trailing edge
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WO2021180559A1 (fr) 2021-09-16
CA3184635A1 (fr) 2021-09-16
CN115559934A (zh) 2023-01-03
DE102021105225A1 (de) 2021-09-16
CN115190945A (zh) 2022-10-14
CN115653919A (zh) 2023-01-31
EP4083432A1 (fr) 2022-11-02
US11965521B2 (en) 2024-04-23
WO2021180560A1 (fr) 2021-09-16
KR20220146705A (ko) 2022-11-01
US11988224B2 (en) 2024-05-21
EP4034769A1 (fr) 2022-08-03
KR20220151219A (ko) 2022-11-14
KR20220146472A (ko) 2022-11-01
KR20220150292A (ko) 2022-11-10
US20230132350A1 (en) 2023-04-27
US20240084815A1 (en) 2024-03-14
CN115176088A (zh) 2022-10-11
CA3184944A1 (fr) 2021-09-16
EP4034770A1 (fr) 2022-08-03
CA3168948A1 (fr) 2021-09-16
US20230003229A1 (en) 2023-01-05
CA3168950A1 (fr) 2021-09-16
US20230138644A1 (en) 2023-05-04

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